EP2907975B1 - Aube à revêtement polymère avec bout d'aube abrasive - Google Patents

Aube à revêtement polymère avec bout d'aube abrasive Download PDF

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Publication number
EP2907975B1
EP2907975B1 EP15154887.2A EP15154887A EP2907975B1 EP 2907975 B1 EP2907975 B1 EP 2907975B1 EP 15154887 A EP15154887 A EP 15154887A EP 2907975 B1 EP2907975 B1 EP 2907975B1
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EP
European Patent Office
Prior art keywords
rotor system
recited
fan rotor
metal
abrasive tip
Prior art date
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Active
Application number
EP15154887.2A
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German (de)
English (en)
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EP2907975A1 (fr
Inventor
Christopher W. Strock
Russell A. Beers
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RTX Corp
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United Technologies Corp
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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/20—Specially-shaped blade tips to seal space between tips and stator
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
    • F01D11/12—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part
    • F01D11/122—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part with erodable or abradable material
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/28—Selecting particular materials; Particular measures relating thereto; Measures against erosion or corrosion
    • F01D5/284—Selection of ceramic materials
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/28—Selecting particular materials; Particular measures relating thereto; Measures against erosion or corrosion
    • F01D5/288—Protective coatings for blades
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
    • F02C3/04—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor
    • F02C3/10—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor with another turbine driving an output shaft but not driving the compressor
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K3/00—Plants including a gas turbine driving a compressor or a ducted fan
    • F02K3/02—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber
    • F02K3/04—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type
    • F02K3/06—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type with front fan
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/26—Rotors specially for elastic fluids
    • F04D29/32—Rotors specially for elastic fluids for axial flow pumps
    • F04D29/321—Rotors specially for elastic fluids for axial flow pumps for axial flow compressors
    • F04D29/324—Blades
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2230/00—Manufacture
    • F05D2230/30—Manufacture with deposition of material
    • F05D2230/31—Layer deposition
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2230/00—Manufacture
    • F05D2230/90—Coating; Surface treatment
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2240/00—Components
    • F05D2240/20—Rotors
    • F05D2240/30—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor
    • F05D2240/307—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor related to the tip of a rotor blade
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/10—Metals, alloys or intermetallic compounds
    • F05D2300/12—Light metals
    • F05D2300/121—Aluminium
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/10—Metals, alloys or intermetallic compounds
    • F05D2300/17—Alloys
    • F05D2300/173—Aluminium alloys, e.g. AlCuMgPb
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/20—Oxide or non-oxide ceramics
    • F05D2300/21—Oxide ceramics
    • F05D2300/2112—Aluminium oxides
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Definitions

  • This disclosure relates to abrasive tips for rotatable blades.
  • Abradable seals or coatings can be used to protect moving parts from damage during rub interaction while providing a small clearance.
  • Such seals are used in turbomachines to interface with abrasive tips of a rotating blade stage.
  • US 2014/0010663 A1 describes a method of manufacturing a fan blade.
  • a fan rotor system in accordance with claim 1.
  • the metal matrix and the metal-based material are compositionally composed of the same predominant metal.
  • the metal is aluminum.
  • the metal matrix is a eutectic aluminum-silicon alloy.
  • the metal matrix of the abrasive tip interfaces with the metal-based material.
  • the metal matrix is aluminum and the hard particles include alumina.
  • the metal matrix is aluminum and the hard particles include zirconia.
  • the abrasive tip includes, by volume, 0.1-50% of the hard particles.
  • the abrasive tip includes, by volume, 5-15% of the hard particles.
  • the abrasive tip has a thickness in a thickness range of 0.025-1.3 millimeters, the hard particles have an average maximum dimension in a particle size range of 10-200 micrometers but not exceeding the thickness.
  • the hard particles are faceted.
  • a further embodiment of any of the foregoing embodiments includes a bonding agent selected from the group consisting of a metallic bond coat, a polymeric material, and combinations thereof.
  • the bonding agent includes the polymeric material, the polymeric material forming a layer having a thickness of 0.0254 - 3.175 mm.
  • a gas turbine engine includes a compressor section, a combustor in fluid communication with the compressor section, a turbine section in fluid communication with the combustor, and a fan rotatably coupled with the turbine section.
  • the fan includes a plurality of circumferentially-spaced rotatable blades as recited in claim 1, and a seal circumscribing the plurality of circumferentially-spaced rotatable blades. The seal is contactable with, and abradable by, the abrasive tip.
  • FIG. 1 schematically illustrates a gas turbine engine 20.
  • the gas turbine engine 20 is disclosed herein as a two-spool turbofan that generally incorporates a fan section 22, a compressor section 24, a combustor section 26 and a turbine section 28.
  • Alternative engines might include an augmentor section (not shown) among other systems or features.
  • the fan section 22 drives air along a bypass flow path B in a bypass duct defined within a fan case 15, and into a core flow path C to the compressor section 24 for compression and communication into the combustor section 26 then expansion through the turbine section 28.
  • the exemplary engine 20 generally includes a low speed spool 30 and a high speed spool 32 mounted for rotation about an engine central longitudinal axis A relative to an engine static structure 36 via several bearing systems 38. It should be understood that various bearing systems 38 at various locations may alternatively or additionally be provided, and the location of bearing systems 38 may be varied as appropriate to the application.
  • the low speed spool 30 generally includes an inner shaft 40 that interconnects a fan 42, a first (or low) pressure compressor 44 and a first (or low) pressure turbine 46.
  • the inner shaft 40 is connected to the fan 42 through a speed change mechanism, which in exemplary gas turbine engine 20 is illustrated as a geared architecture 48 to drive the fan 42 at a lower speed than the low speed spool 30.
  • the high speed spool 32 includes an outer shaft 50 that interconnects a second (or high) pressure compressor 52 and a second (or high) pressure turbine 54.
  • a combustor 56 is arranged in exemplary gas turbine 20 between the high pressure compressor 52 and the high pressure turbine 54.
  • a mid-turbine frame 57 of the engine static structure 36 is arranged generally between the high pressure turbine 54 and the low pressure turbine 46.
  • the mid-turbine frame 57 further supports bearing systems 38 in the turbine section 28.
  • the inner shaft 40 and the outer shaft 50 are concentric and rotate via bearing systems 38 about the engine central longitudinal axis A which is collinear with their longitudinal axes.
  • the core airflow is compressed by the low pressure compressor 44 then the high pressure compressor 52, mixed and burned with fuel in the combustor 56, then expanded over the high pressure turbine 54 and low pressure turbine 46.
  • the mid-turbine frame 57 includes airfoils 59 which are in the core airflow path C.
  • the turbines 46, 54 rotationally drive the respective low speed spool 30 and high speed spool 32 in response to the expansion.
  • gear system 48 may be located aft of combustor section 26 or even aft of turbine section 28, and fan section 22 may be positioned forward or aft of the location of gear system 48.
  • the engine 20 in one example is a high-bypass geared aircraft engine.
  • the engine 20 bypass ratio is greater than about six (6), with an example embodiment being greater than about ten (10)
  • the geared architecture 48 is an epicyclic gear train, such as a planetary gear system or other gear system, with a gear reduction ratio of greater than about 2.3 and the low pressure turbine 46 has a pressure ratio that is greater than about five.
  • the engine 20 bypass ratio is greater than about ten (10:1)
  • the fan diameter is significantly larger than that of the low pressure compressor 44
  • the low pressure turbine 46 has a pressure ratio that is greater than about five (5:1).
  • Low pressure turbine 46 pressure ratio is pressure measured prior to inlet of low pressure turbine 46 as related to the pressure at the outlet of the low pressure turbine 46 prior to an exhaust nozzle.
  • the geared architecture 48 may be an epicycle gear train, such as a planetary gear system or other gear system, with a gear reduction ratio of greater than about 2.3:1. It should be understood, however, that the above parameters are only exemplary of one embodiment of a geared architecture engine and that the present invention is applicable to other gas turbine engines including direct drive turbofans.
  • the fan section 22 of the engine 20 is designed for a particular flight condition -- typically cruise at about 0.8 Mach and about 35,000 feet (10668 m).
  • the flight condition of 0.8 Mach and 35,000 ft, with the engine at its best fuel consumption - also known as "bucket cruise Thrust Specific Fuel Consumption" (TSFC) - is the industry standard parameter of lbm of fuel being burned divided by lbf of thrust the engine produces at that operating point.
  • TSFC Thrust Specific Fuel Consumption
  • Low fan pressure ratio is the pressure ratio across the fan blade alone, without a Fan Exit Guide Vane (“FEGV”) system.
  • the low fan pressure ratio as disclosed herein according to one non-limiting embodiment is less than about 1.45.
  • Low corrected fan tip speed is the actual fan tip speed in ft/sec divided by an industry standard temperature correction of [(Tram °R) / (518.7 °R)] 0.5 .
  • the "Low corrected fan tip speed” as disclosed herein according to one non-limiting embodiment is less than about 1150 ft / second (350.5 m/s).
  • FIG. 2 illustrates an isolated view of the fan section 22 of the engine 20.
  • the fan 42 includes a rotor 60 that has a plurality of circumferentially-spaced blades 62.
  • Each blade 62 includes an airfoil section 64 that extends between leading and trailing edges 66/68, first and second opposed sides 70/72 that each joins the leading and trailing edges 66/68, and an inner end 74 and a free tip end 76.
  • Each blade includes an abrasive tip 78 at the free tip end 76.
  • the fan case 15 is annular in shape and circumscribes the blades 62.
  • the fan section 22 is designed such that the abrasive tips 78 of the blades 62 rub against the fan case 15 during rotation.
  • the fan case 15 includes an abradable seal 80 mounted on a radially inner side of the fan case 15.
  • the abradable seal 80 is formed of a polymeric-based material, such as a polymer matrix composite.
  • the polymer matrix composite includes an epoxy matrix and a silica-containing filler dispersed through the matrix.
  • the silica-containing filler is or includes hollow glass microspheres.
  • An example is 3MTM Scotch-WeldTM Structural Void Filling Compound EC-3555.
  • abradable refers to the one of the two components that wears, while the other component is “abrasive” and does not wear or wears less.
  • abrasive tips 78 of the blades 62 rub against the seal 80, the seal 80 will be worn whereas the abrasive tips 78 will not wear or will wear less than the seal 80.
  • the word “abrasive” thus also implies that there is or can be contact with an abradable component.
  • Figure 3 shows a cutaway view of a representative portion of the airfoil section 64 of one of the blades 62 and a portion of the abradable seal 80.
  • the airfoil section 64 is formed of a metal-based material with a polymeric overcoat 62a on the surfaces thereof.
  • the polymeric overcoat 62a serves to protect the underlying airfoil section 64 from erosion due to foreign particulate ingested into the engine 20.
  • the metal-based material of the airfoil section 64 is an aluminum alloy.
  • the polymeric coating 62a can be a polyurethane-based coating, an epoxy-based coating, or a silicone rubber-based coating, but is not limited to these types of polymeric coatings or materials.
  • the polymeric coating 62a can cover the first and second sides 70/72 of the blades 62 and can span the entire lateral surface of the blade 62 between the leading and trailing edges 66/68.
  • Friction between a blade tip and a surrounding case generates heat.
  • the heat can be conducted into the case, into the blade, or both.
  • the metal of the blade is generally a better thermal conductor than the polymer of the case, and a majority of the heat thus can conduct into the blade. While this may normally not present any detriments for a plain metal blade, the heat conduction can be detrimental to a metal blade that has a polymeric overcoat because the heat can cause delamination of the polymeric overcoat and thus compromise the erosion protection.
  • the abrasive tip 78 has a composition selected with respect to heat-induced delamination of the polymeric overcoat 62a from frictional heat generated during rubbing between the abrasive tip 78 and the abradable seal 80. That is, the respective compositions of the abradable seal 80 and the abrasive tip 78 are complementarily selected with respect to frictional heat generated and heat-induced delamination of the polymeric overcoat 62a.
  • the compositions are selected with regard to a blade temperature at which the polymeric overcoat 62a does not delaminate or has a defined delamination durability over an extended period of time, such as the life of the engine 20.
  • Figure 4 illustrates a cross-section of representative portion of a further example of the abrasive tip 78.
  • the abrasive tip 78 includes a metal matrix 90 and hard particles 92 dispersed through the metal matrix 90.
  • the metal matrix 90 and the metal-based material of the airfoil section 64 are compositionally composed of the same predominant metal, which can promote strong adhesion if the abrasive tip 78 interfaces with the metal-based material (i.e., the abrasive tip 78 is in direct contact with the metal-based material, as depicted in Figure 4 ).
  • the metal can be aluminum.
  • the metal matrix 90 is a eutectic aluminum-silicon alloy having a composition, by atomic weight, of 88% aluminum and 12% silicon.
  • the eutectic composition provides high hardness and strength to enhance holding the hard particles 92 in the metal matrix 90.
  • the eutectic composition also has good high temperature properties and retains strength at high temperatures rather than softening.
  • the metal matrix 90 is, or predominantly includes, aluminum, and the hard particles 92 are, or predominantly include, alumina (Al 2 O 3 ). In an additional example, the hard particles 92 are, or predominantly include, zirconia (ZrO 2 ). In yet another example, the hard particles 92 are, or predominantly include, alumina and zirconia.
  • the hard particles 92 are not limited to alumina and zirconia, and other oxides, nitrides, carbides, oxycarbides, oxynitrides, diamond and combinations thereof can be used selectively, with respect to heat-induced delamination of the polymeric overcoat 62a from frictional heat generated during rubbing between the abrasive tip 78 and the abradable seal 80.
  • the abrasive tip 78 can have a thickness in a thickness range of 0.025-1.3 millimeters, and the hard particles 92 can have an average maximum dimension in a particle size range of 10-200 micrometers.
  • the hard particles 92 may protrude from the metal matrix 90 or be completely covered by the metal matrix.
  • a polymer matrix filled with hollow glass microspheres for the abradable seal 80 is complimentary with a metal matrix 90 of aluminum and hard particles 92 of alumina, zirconia, or both in the abrasive tip 78, with respect to frictional heat generated and heat-induced delamination of the polymeric overcoat 62a. That is, the frictional heat generated between the abradable seal 80 and the abrasive tip 78 cause a blade 62 temperature at which the example polymer of the polymeric overcoat 62a does not delaminate, or at least meets a delamination durability over an extended period of time, such as the life of the engine 20.
  • the abrasive tip 78 includes, by volume, 0.1-50% of the hard particles 92.
  • an amount by volume of 5-15% of the hard particles 92 can be used.
  • the hard particles 92 are faceted and thus have angled facets 92a.
  • the angled facets 92a provide relatively sharp corners that facilitate efficient "cutting" through the abradable seal 80 with low cutting forces, which lowers frictions and, in turn, contributes to lowering the amount of heat generated.
  • the hard particles 92 are DURALUM ATZ II that have approximately 40% tetragonal zirconia with titania evenly distributed throughout the individual alumina grains.
  • an optional bonding agent 96 serves to facilitate bonding between the abrasive tip 78 and the metal-based material of the airfoil section 64.
  • the bonding agent 96 is a metallic bond coat that is located primarily between the abrasive tip 78 and the metal-based material of the airfoil section 64 and serves to enhance adhesion.
  • the metallic bond coat can be, or can predominantly include, nickel and aluminum.
  • the metallic bond coat can be excluded and a bonding agent 96 of an adhesive/sealant material can be used instead to improve corrosion resistance in the presence of moisture and also increase bonding strength.
  • the adhesive/sealant material can be a polymeric-based material, such as, but not limited to, an epoxy or an epoxy-based material.
  • the adhesive/sealant material can infiltrate or partially infiltrate into pores of the abrasive tip 78 such that the abrasive tip 78, or at least a portion thereof, and the underlying airfoil section 64 are protected from corrosion.
  • the abrasive tip 78 can be primarily directly bonded to the metal-based material of the airfoil section 64, and the adhesive/sealant can fill or partially fill gaps or pores along the interface of the abrasive tip 78 and the underlying airfoil section 64 to further enhance adhesion.
  • the adhesive/sealant could be, or could additionally be used as, an over-layer on top of the abrasive tip 78 to help close the tip gaps to the abradable seal 80, such as for the shorter blades. On longer blades the adhesive/sealant may rapidly wear down until the abrasive tip 78 starts cutting the abradable seal 80.
  • the adhesive/sealant can have an over-layer thickness of 0.0254 - 3.175 millimeters, and in some examples a thickness of 0.254 - 1.27 millimeters.
  • the abrasive tip 78 can be a coating that is deposited onto the airfoil section 64, or metallic bond coat 96, if used.
  • a thermal spray technique can be used, in which one or more feedstocks are fed into a thermal plume.
  • the feedstock can include individual powder feedstocks of the metal of the metal matrix 90 and the hard particles 92, or a single mixed feedstock powder of the metal of the metal matrix 90 and the hard particles 92.
  • the powder feedstock can include composite particles of the metal of the metal matrix 90 and the hard particles 92.
  • Composite particles can include the metal and hard particles 92 in agglomeration or structured particles that have a hard particle 92 core and the metal overcoated around the core.
  • the hard particles 92 are not melted during the thermal spray deposition.
  • the deposition process can be controlled to avoid melting or substantial melting, to ensure that the hard particles 92 retain the faceted geometry described above. It is desirable to retain as much of the faceted geometry as possible so that the cutting forces and heat generation are minimized during rub contact.
  • the abrasive tip 78 can be pre-fabricated and then attached to the airfoil section 64, such as with an adhesive.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Materials Engineering (AREA)
  • Combustion & Propulsion (AREA)
  • Ceramic Engineering (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Claims (15)

  1. Système de rotor de soufflante comprenant :
    une pluralité d'aubes rotatives espacées circonférentiellement (62),
    un joint (80) entourant la pluralité d'aubes rotatives espacées circonférentiellement (62), le joint (80) pouvant être mis en contact avec le bout abrasif (78) et abrasé par celui-ci, dans lequel
    les compositions respectives du joint (80) et du bout abrasif (78) sont choisis de manière complémentaire par rapport à la chaleur de frottement générée et à la délamination induite par la chaleur du revêtement de finition polymère (62a), et
    dans lequel chacune des aubes est une aube (62) comprenant :
    une section de profil (64) s'étendant entre les bords d'attaque et de fuite (66, 68), les premier et second côtés opposés (70, 72) joignant chacun les bords d'attaque et de fuite (66, 68), et une extrémité interne (74) et une extrémité de bout libre (76),
    la section de profil (64) étant formée d'un matériau à base de métal avec un revêtement de finition polymère (62a) sur au moins l'un du bord d'attaque (66), du bord de fuite (68), du premier côté (70) et du second côté (72), la section de profil (64) incluant un bout abrasif (78) au niveau de l'extrémité de bout libre (76),
    caractérisé en ce que
    le bout abrasif (78) inclut une matrice métallique (90) et des particules dures (92) dispersées à travers la matrice métallique (90), et en ce que
    le joint est formé d'un composite à matrice polymère.
  2. Système de rotor de soufflante selon la revendication 1, dans lequel la matrice métallique (90) et le matériau à base métallique sont composés du point de vue de la composition du même métal prédominant.
  3. Système de rotor de soufflante selon la revendication 2, dans lequel le métal est de l'aluminium.
  4. Système de rotor de soufflante selon la revendication 3, dans lequel la matrice métallique (90) est un alliage aluminium-silicium eutectique.
  5. Système de rotor de soufflante selon la revendication 1, 2 ou 3, dans lequel la matrice métallique (90) est de l'aluminium et les particules dures (92) incluent de l'alumine.
  6. Système de rotor de soufflante selon la revendication 1, 2, 3 ou 4, dans lequel la matrice métallique (90) est de l'aluminium et les particules dures (92) incluent de la zircone.
  7. Système de rotor de soufflante selon l'une quelconque des revendications 1 à 6, dans lequel le bout abrasif (78) inclut, en volume, 0,1 à 50 % des particules dures (92), par exemple en volume, 5 à 15 % des particules dures (92).
  8. Système de rotor de soufflante selon l'une quelconque des revendications 1 à 7, dans lequel le bout abrasif (78) a une épaisseur dans une plage d'épaisseur de 0,025 à 1,3 millimètres, les particules dures (92) ont une dimension maximale moyenne dans une plage de taille de particules de 10 à 200 micromètres mais ne dépassant pas l'épaisseur.
  9. Système de rotor de soufflante selon l'une quelconque des revendications 1 à 8, dans lequel les particules dures (92) sont à facettes.
  10. Système de rotor de soufflante selon l'une quelconque des revendications 1 à 9, dans lequel la matrice métallique (90) du bout abrasif (78) interagit avec le matériau à base de métal.
  11. Système de rotor de soufflante selon l'une quelconque des revendications 1 à 9, comprenant en outre un agent liant (96) choisi dans le groupe constitué d'un revêtement de liaison métallique, d'un matériau polymère, et de combinaisons de ceux-ci.
  12. Système de rotor de soufflante selon la revendication 11, dans lequel l'agent liant (96) inclut le matériau polymère, le matériau polymère formant une couche ayant une épaisseur de 0,0254 à 3,175 mm.
  13. Système de rotor de soufflante selon l'une quelconque des revendications précédentes, dans lequel le joint comprend une matrice époxy et une charge contenant de la silice dispersée à travers la matrice.
  14. Système de rotor de soufflante selon la revendication 13, dans lequel la charge contenant de la silice est ou inclut des microsphères de verre creuses.
  15. Turbine à gaz (20) comprenant :
    une section de compresseur (24) ;
    une chambre de combustion (26) en communication fluidique avec la section de compresseur (24) ;
    une section de turbine (28) en communication fluidique avec la chambre de combustion (26) ;
    une soufflante (22) couplée de manière rotative à la section de turbine (28), la soufflante (22) incluant une pluralité d'aubes rotatives espacées circonférentiellement (62), chacune des aubes (62) étant une aube (62) selon l'une quelconque des revendications précédentes ; et
    un joint (80) entourant la pluralité d'aubes rotatives espacées circonférentiellement (62), le joint (80) pouvant être mis en contact avec le bout abrasif (78) et abrasé par celui-ci.
EP15154887.2A 2014-02-14 2015-02-12 Aube à revêtement polymère avec bout d'aube abrasive Active EP2907975B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US201461939923P 2014-02-14 2014-02-14
US14/592,933 US10221698B2 (en) 2014-02-14 2015-01-09 Polymer-coated blade with abrasive tip

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EP2907975A1 EP2907975A1 (fr) 2015-08-19
EP2907975B1 true EP2907975B1 (fr) 2018-05-09

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FR3051829B1 (fr) * 2016-05-24 2018-05-25 Safran Aircraft Engines Procede de fabrication d'un carter annulaire equipe de turbomachine
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FR3095650B1 (fr) * 2019-05-02 2021-04-09 Safran Aircraft Engines Procédé de revêtement d’une pièce de turbomachine d’aéronef
US11365632B2 (en) * 2020-05-22 2022-06-21 Raytheon Technologies Corporation Blade with abrasive tip
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Also Published As

Publication number Publication date
EP2907975A1 (fr) 2015-08-19
US20150233255A1 (en) 2015-08-20
US20190195075A1 (en) 2019-06-27
US10221698B2 (en) 2019-03-05

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